A vibration reduction and shock resistance method and system for aerospace sensors

Abstract

This invention discloses a vibration reduction and shock-resistant method and system for aerospace sensors in the field of aerospace equipment technology. The system includes a bracket and a sensor mounting base, which are fixedly connected by a first bolt. A vibration reduction and shock-resistant device is sleeved on the portion of the first bolt located between the bracket and the sensor mounting base. The vibration reduction and shock-resistant device includes a sleeve sleeved on the first bolt, with the inner wall of the sleeve threadedly connected to the first bolt. An end cap is threadedly connected to the middle of the outer wall of the sleeve, completely enclosing the lower part of the sleeve. A vibration reduction and shock-resistant space is left between the outer wall of the sleeve and the inner wall of the end cap. A multi-layered vibration reduction and shock-resistant structure resembling a woodpecker is provided within the vibration reduction and shock-resistant space. The multi-layered vibration reduction and shock-resistant structure resembling a woodpecker includes a beak layer, a hyoid bone layer, a cancellous layer, and a cranial cerebrospinal fluid layer arranged sequentially from the outer wall of the sleeve to the inner wall of the end cap. This solution, based on the vibration reduction mechanism of a woodpecker's head, can effectively disperse residual energy, allowing impact energy to be transmitted in multiple directions.

Description

Technical Field

[0001] This invention belongs to the field of aerospace equipment technology, specifically a vibration reduction and shock resistance method and system for aerospace sensors. Background Technology

[0002] Aerospace equipment operates in harsh environments, including those of aero-engines and the entire machine, which are subject to various high-frequency and low-frequency vibrations. Aerospace equipment is equipped with a number of accessories and sensors, which have high requirements for vibration environment. Therefore, the design of vibration reduction support structures for accessories and sensors has always been a challenge for the design of sensor support structures in aerospace applications.

[0003] Existing design methods for vibration reduction and shock resistance of aerospace sensors mainly involve introducing vibration reduction and shock resistance designs into the support structure to isolate the sensor from vibration transmission to aerospace equipment. For example, Chinese Patent Publication No. CN 206111937 U discloses a vibration reduction device for a sensor mounting bracket, including: a sensor mounting base, a bracket, a first sleeve, a first rubber vibration damping pad, a first gasket, an end cap, a second sleeve, a second rubber vibration damping pad, a second gasket, a pressure plate, rivets, bolts, and self-locking nuts. This device uses a rubber vibration damping combination structure on the upper surface of the bracket, which has good vibration reduction capability in the sensor mounting direction. At the same time, the rubber vibration damping pad is made of materials such as silicone rubber, which can maintain good elasticity and has the advantages of high temperature resistance and long service life.

[0004] This device achieves vibration reduction and shock resistance through the material properties of rubber damping pads and a double-layer structure of rubber damping pads and gaskets (mainly relying on the material properties of rubber). However, in our research, in addition to optimizing the properties of the material itself, we can also continuously optimize the multi-layer structure based on the transmission characteristics of stress waves. Therefore, we propose a vibration reduction and shock resistance method and system for aerospace sensors. Summary of the Invention

[0005] The purpose of this invention is to provide a vibration reduction and shock resistance method and system for aerospace sensors to solve the problems existing in the prior art.

[0006] To achieve the above objectives, the technical solution of the present invention is as follows: A vibration reduction and shock-resistant system for aerospace sensors, comprising:

[0007] The bracket is installed on the housing of the aerospace equipment;

[0008] Sensor mounting bracket for mounting sensors;

[0009] The bracket and the sensor mounting base are fixedly connected by a first bolt. The portion of the first bolt located between the bracket and the sensor mounting base is fitted with a vibration damping and impact-resistant device. The vibration damping and impact-resistant device includes a sleeve fitted on the first bolt. The inner wall of the sleeve is threaded to the first bolt. An end cap is threaded to the middle of the outer wall of the sleeve. The end cap completely covers the lower part of the sleeve. A vibration damping and impact-resistant space is left between the outer wall of the sleeve and the inner wall of the end cap. A multi-layer vibration damping and impact-resistant structure imitating a woodpecker is provided in the vibration damping and impact-resistant space.

[0010] The woodpecker-inspired multi-layered vibration-damping and shock-resistant structure includes, sequentially arranged from the outer wall of the sleeve to the inner wall of the end cap, a beak layer, a hyoid bone layer, a cancellous layer, and a skull cerebrospinal fluid layer:

[0011] The beak layer includes vibration isolation groups that are evenly distributed vertically along the outer wall of the sleeve. Each vibration isolation group includes wire rope vibration isolators that are evenly distributed circumferentially along the outer wall of the sleeve. One side of the wire rope vibration isolator is hinged to the outer wall of the sleeve, and the other side of the wire rope vibration isolator is connected to the hyoid layer through a first wire rope. The first wire rope is slidably connected to the hyoid layer. Adjacent wire rope vibration isolators in the vertical direction along the outer wall of the sleeve are connected through a second wire rope. The wire rope vibration isolators, the first wire rope, and the second wire rope form a beak shape.

[0012] The hyoid bone layer includes a rubber plate;

[0013] The loose layer includes foam board;

[0014] The cerebrospinal fluid layer of the skull includes silica particles that fill the space between the foam layer and the inner wall of the endcap.

[0015] The principles and beneficial effects of this solution:

[0016] When energy from the direction of the aerospace equipment shell impacts the aerospace equipment shell and sensor, the impact energy is transmitted from the bracket to the sensor along the direction of the first bolt. During the transmission process, when the impact energy is transmitted to the steel wire rope vibration isolator of the first layer, as the steel wire rope deforms, there will be friction between the wires and strands of the steel wire rope, which absorbs a lot of the impact energy and has a strong vibration isolation capability.

[0017] Part of the remaining impact energy after passing through the first layer of wire rope vibration isolators is transmitted along the first wire rope to the rubber plate. Due to the lightweight nature of the rubber plate and its numerous microporous structures, it can absorb the impact energy, achieving vibration damping while simultaneously dispersing the energy. This dispersed energy continues to propagate towards the foam board, where the silica particles filling the space between the foam board and the inner wall of the end cap further absorb the dispersed impact energy.

[0018] Of the remaining impact energy after passing through the first layer of wire rope vibration isolators, another portion is transmitted along the second wire rope to the next layer of wire rope vibration isolators. Using the same principle as the first layer of wire rope vibration isolators, vibration damping and shock resistance are achieved. Therefore, during the transmission of impact energy from the bracket to the sensor mounting base, a portion of the impact energy can be consumed by the wire rope vibration isolators. The remaining impact energy can then be transmitted through the first and second wire ropes to the rubber plate and the next layer of wire rope vibration isolators, respectively, to continue consuming energy, ensuring that the energy reaching the sensor does not damage it.

[0019] This solution incorporates a shock-absorbing and impact-resistant device based on the woodpecker's head vibration reduction mechanism between the bracket and the sensor mounting base. Compared with existing technologies, it has the following advantages:

[0020] 1. Existing technology uses a double-layer structure consisting of rubber damping pads and gaskets. It primarily utilizes the material properties of rubber to reduce the impact energy transmitted from the aerospace equipment direction to the sensor direction, thus protecting the sensor. However, during the impact energy transmission process, the rubber damping pads gradually lose elasticity over time and with increasing impact frequency. Furthermore, the impact energy on the rubber damping pads is unidirectional; being constantly subjected to force in the same direction accelerates the damage to the rubber damping pads, thereby affecting the service life of the vibration damping device. This solution uses steel wire rope vibration isolators to absorb the impact energy first. Since the tensile and compressive strength of steel wire ropes is superior to that of rubber pads, when impact energy strikes the steel wire rope vibration isolator, the friction between the steel wire ropes absorbs the impact energy. A significant amount of energy is transferred to the rubber sheet, foam board, and silica particles in sequence, reducing the direct impact on the rubber sheet. When impacted, the silica particles become fluid, and during this flow, a large amount of energy is consumed through collisions and friction between particles and between particles and the inner wall of the end cap, reducing the energy that the sensor can receive. Furthermore, due to their characteristics, the foam board and silica particles can store energy first and then slowly release it. The energy released by the foam board and silica particles then acts in the opposite direction on the rubber sheet, which can prevent the rubber sheet from being subjected to long-term energy impact from a single direction, thus shortening its service life and affecting the performance of the entire vibration damping device.

[0021] 2. This solution is based on the vibration reduction mechanism of a woodpecker's head. The steel wire rope vibration isolators are connected to the rubber plate by a first steel wire rope, and adjacent steel wire rope vibration isolators are connected by a second steel wire rope. The first and second steel wire ropes form a certain angle. After the steel wire rope vibration isolators of the first layer absorb some energy upon impact, the remaining energy is partially transferred to the rubber plate through the first steel wire rope and partially transferred to the steel wire rope vibration isolators of the next layer through the second steel wire rope. This can effectively disperse the remaining energy, allowing the impact energy to be transmitted in multiple directions. This can absorb as much energy as possible to protect the sensor from damage, and also avoid excessive energy on a single vibration damping device, thus extending the service life of the entire vibration damping and impact-resistant device.

[0022] Furthermore, when the first wire rope slides along the rubber plate, the angle between the first wire rope and the second wire rope is α, and the range of α is 30-60°. In the initial state, the angle between the first wire rope and the second wire rope is 60°.

[0023] Beneficial effects: When the impact energy from the wire rope vibration isolator continues to be transmitted along the first wire rope, since the initial angle between the first and second wire ropes is 60°, and the force direction of the impact energy is mainly from the support to the sensor mounting base, the force of the impact energy on the first wire rope causes it to slide towards the sensor. This gradually reduces the angle between the first and second wire ropes, prolonging the friction between the first wire rope and the impact energy, absorbing the impact energy as much as possible, and preventing excessive impact energy from rapidly impacting the rubber plate and causing it to lose its function prematurely. Elasticity; and the initial state of the first wire rope is set to 60° to avoid an excessively large angle. If the impact energy is applied perpendicularly to the first wire rope, it is easy to break the first wire rope, and it is also not conducive to the dispersion of impact energy along the direction of the first wire rope. The movement range of the first wire rope is limited to forming a 30° angle with the second wire rope to avoid an excessively small angle. If the impact energy is transmitted too much along the direction of the next layer of wire rope vibration isolator, it is not conducive to the transmission of impact energy along the direction of the first wire rope to the rubber plate. This would result in the next layer of wire rope vibration isolator bearing too much impact energy, affecting its service life.

[0024] Furthermore, the silica particle filling rate in the cerebrospinal fluid layer of the skull is 50%-70%.

[0025] Beneficial effects: The filling rate of silica particles in the cerebrospinal fluid layer of the skull is set at 50%-70%. Too little or too much silica particles will affect the collision frequency between particles and between particles and the inner wall of the end cap, resulting in the impact energy not being fully absorbed.

[0026] Furthermore, adjacent wire rope vibration isolators along the circumference of the outer wall of the sleeve are connected by a third wire rope.

[0027] Beneficial effects: The steel wire rope vibration isolators on the same layer are connected by a third steel wire rope, which allows the impact energy received by the steel wire rope vibration isolators to be transmitted laterally. When the third steel wire rope is subjected to the impact energy transmitted by the steel wire rope vibration isolators on both sides, they can cancel each other out after colliding because their directions are opposite, which further reduces the impact energy received by the sensor and improves the safety of the sensor.

[0028] Furthermore, a pressure plate is bonded between the end cap and the bracket on the side facing the bracket. The end cap has an inverted T-shaped cross-section and includes an integrally formed first boss and a second boss. The second boss, the pressure plate, and the bracket are coaxially formed with threaded holes along the vertical axis. Several threaded holes are provided along the circumference of the second boss, and the threaded holes are threadedly connected to a second bolt.

[0029] Beneficial effect: By placing a pressure plate between the end cap and the bracket and then fixing the connection with a second bolt, the overall device can be reinforced and the device can be prevented from becoming unstable when subjected to impact.

[0030] Furthermore, a vibration reduction and shock resistance method for aerospace sensors includes the following steps:

[0031] S1. Construct a vibration reduction and shock resistance system based on ANSYS finite element analysis software, and design and optimize the objective function of the wire rope vibration isolator based on the vibration reduction and shock resistance system.

[0032] S2. Simulate the seismic source and measure the pre-control structural response signal of the vibration reduction and shock resistance system, as well as the frequency transfer function from the seismic source to the wire rope vibration isolator.

[0033] S3. Construct a fitness function based on the objective function. Select n wire rope vibration isolators from the vibration reduction and shock resistance system and perform genetic algorithm iteration. Calculate the fitness function corresponding to the current iteration based on the frequency transfer function. If the fitness function of the current iteration and the previous iteration meet the set requirements, then the number and position of the selected wire rope vibration isolators are taken as the optimal value, where 0 < n ≤ m.

[0034] S4. Based on the number and location of the wire rope vibration isolators obtained in S3, install the wire rope vibration isolators on the outer wall of the sleeve, connect the sleeve and the end cap, and complete the assembly of the woodpecker-inspired multi-layer vibration reduction and impact resistance structure in the vibration reduction and impact resistance system.

[0035] S5. Install the bracket, pressure plate, woodpecker-inspired multi-layer vibration damping and shock-resistant structure and sensor mounting base in sequence to achieve vibration damping and shock resistance for aerospace sensors based on the woodpecker head vibration damping mechanism.

[0036] Furthermore, in S1 and S2, the control objective is set to the sum of squares of the responses of m wire rope vibration isolators, e m The structure response signal after control, d m To control the pre-structural response signal, u p For impact energy, G mp Let be the frequency transfer function, then the expression for the objective function is:

[0037] e m =d m +G mp u p ;

[0038] J = e m H e m ;

[0039] The optimal impact energy is obtained by minimizing the control objective:

[0040] u p,opt=-(G mp H G mp ) -1 G mp d m ;

[0041] The minimum value of the objective function of the vibration reduction and shock resistance system is:

[0042] J min =(d m +G mp u p,opt ) H (d m +G mp u p,opt ).

[0043] Furthermore, in S3, the expression for the fitness function is:

[0044] F = J min +ωn;

[0045] Where ω is the weighting coefficient of the number n of wire rope vibration isolators.

[0046] Beneficial effects: This method constructs a vibration reduction and shock resistance system based on ANSYS finite element analysis software, and optimizes the number and position of wire rope vibration isolators in its woodpecker-inspired multi-layer vibration reduction and shock resistance structure, making the vibration reduction and shock resistance system in this scheme more versatile. It can adapt to different aerospace sensors for vibration reduction and shock resistance by adjusting the number and position of the wire rope vibration isolators. Attached Figure Description

[0047] Figure 1 This is a cross-sectional view of the aerospace sensor vibration reduction and shock resistance system according to an embodiment of the present invention.

[0048] Figure 2 This is a schematic flowchart of the vibration reduction and shock resistance method for aerospace sensors according to an embodiment of the present invention. Detailed Implementation

[0049] The following detailed description illustrates the specific implementation method:

[0050] The reference numerals in the accompanying drawings include: bracket 1, sensor mounting base 2, first bolt 3, sleeve 4, end cap 5, wire rope vibration isolator 6, first wire rope 7, second wire rope 8, rubber sheet 9, foam board 10, silica particles 11, pressure plate 12, and second bolt 13.

[0051] Example 1:

[0052] The basic implementation examples are as follows: Figure 1 As shown: A vibration reduction and shock absorption system for aerospace sensors, comprising:

[0053] Bracket 1 is installed on the housing of the aerospace equipment;

[0054] Sensor mounting bracket 2 is used to mount the sensor;

[0055] The bracket 1 and the sensor mounting base 2 are fixedly connected by the first bolt 3. The part of the first bolt 3 between the bracket 1 and the sensor mounting base 2 is fitted with a vibration damping and impact-resistant device. The vibration damping and impact-resistant device includes a sleeve 4 fitted on the first bolt 3. The inner wall of the sleeve 4 is threaded to the first bolt 3. The middle part of the outer wall of the sleeve 4 is threaded to an end cap 5. The end cap 5 completely covers the lower part of the sleeve 4. A vibration damping and impact-resistant space is left between the outer wall of the sleeve 4 and the inner wall of the end cap 5. A multi-layer vibration damping and impact-resistant structure imitating a woodpecker is provided in the vibration damping and impact-resistant space.

[0056] The woodpecker-inspired multi-layered vibration-damping and shock-resistant structure includes, sequentially arranged from the outer wall of sleeve 4 to the inner wall of end cap 5, a beak layer, a hyoid bone layer, a cancellous layer, and a cranial cerebrospinal fluid layer:

[0057] The beak layer includes vibration isolation groups that are evenly distributed vertically along the outer wall of the sleeve 4. Each vibration isolation group includes wire rope vibration isolators 6 that are evenly distributed circumferentially along the outer wall of the sleeve 4. One side of the wire rope vibration isolator 6 is hinged to the outer wall of the sleeve 4, and the other side of the wire rope vibration isolator 6 is connected to the hyoid layer by a first wire rope 7. The first wire rope 7 is slidably connected to the hyoid layer. Adjacent wire rope vibration isolators 6 in the vertical direction along the outer wall of the sleeve 4 are connected by a second wire rope 8. The wire rope vibration isolators 6, the first wire rope 7, and the second wire rope 8 form a beak shape.

[0058] The hyoid bone layer includes a rubber plate 9;

[0059] The loose layer includes foam board 10;

[0060] The cerebrospinal fluid layer of the skull includes silica particles 11 that fill the space between the foam layer and the inner wall of the end cap 5.

[0061] The specific implementation process is as follows:

[0062] When energy from the direction of the aerospace equipment shell impacts the aerospace equipment shell and sensor, the impact energy is transmitted from the bracket 1 to the sensor along the direction of the first bolt 3. During the transmission process, when the impact energy is transmitted to the steel wire rope vibration isolator 6 of the first layer, as the steel wire rope deforms, there will be friction between the wires and strands of the steel wire rope, which absorbs a lot of the impact energy and has a strong vibration isolation capability.

[0063] Part of the remaining impact energy after passing through the first layer of wire rope vibration isolator 6 is transmitted along the first wire rope 7 to the rubber plate 9. Because the rubber plate 9 is lightweight and has many microporous structures, it can absorb the impact energy to achieve vibration reduction while continuing to disperse the impact energy, allowing it to propagate further towards the foam board 10. The silica particles 11 filling the space between the foam board 10 and the inner wall of the end cap 5 further absorb the dispersed impact energy.

[0064] Another portion of the remaining impact energy after passing through the first layer of wire rope vibration isolators 6 is transmitted along the second wire rope 8 to the next layer of wire rope vibration isolators 6. Using the same principle as the first layer of wire rope vibration isolators 6, vibration reduction and shock resistance are achieved. Therefore, during the transmission of impact energy from the bracket 1 to the sensor mounting base 2, a portion of the impact energy can be consumed by the wire rope vibration isolators 6. The remaining impact energy can be transmitted to the rubber plate 9 and the next layer of wire rope vibration isolators 6 through the first wire rope 7 and the second wire rope 8, respectively, to continue consuming energy, so that the energy that finally reaches the sensor will not damage the sensor.

[0065] Existing technology uses a double-layer structure consisting of rubber damping pads and gaskets. It primarily utilizes the material properties of rubber to reduce the impact energy transmitted from the direction of aerospace equipment to the direction of the sensor, thus protecting the sensor. However, during the impact energy transmission process, the rubber damping pads gradually lose elasticity over time and with increasing impact frequency. Furthermore, the impact energy on the rubber damping pads is unidirectional; being constantly subjected to force in the same direction accelerates the damage to the rubber damping pads, thereby affecting the service life of the vibration damping device. This solution uses a steel wire rope vibration isolator 6 to first absorb the impact energy. Because the tensile and compressive strength of the steel wire rope is superior to that of the rubber pad, when the impact energy strikes the steel wire rope vibration isolator 6, the friction between the steel wire ropes absorbs a significant amount of energy, leaving only the remaining energy... The energy is then transferred sequentially to the rubber plate 9, foam board 10, and silica particles 11, reducing the direct impact on the rubber plate 9. When impacted, the silica particles 11 become fluid. During this flow, a large amount of energy is consumed through collisions and friction between particles and between particles and the inner wall of the end cap 5, reducing the energy that the sensor can receive. Due to their characteristics, the foam board 10 and silica particles 11 can store energy first and then slowly release it. The energy released by the foam board 10 and silica particles 11 then acts in the opposite direction on the rubber plate 9, which can prevent the rubber plate 9 from being subjected to long-term energy impact from a single direction, thus shortening its service life and affecting the performance of the entire vibration damping device.

[0066] This solution is based on the vibration reduction mechanism of a woodpecker's head. The steel wire rope vibration isolator 6 is connected to the rubber plate 9 by a first steel wire rope 7, and adjacent steel wire rope vibration isolators 6 are connected by a second steel wire rope 8. The first steel wire rope 7 and the second steel wire rope 8 form a certain angle. After the steel wire rope vibration isolator 6 of the first layer absorbs part of the energy upon impact, the remaining energy is partially transferred to the rubber plate 9 through the first steel wire rope 7, and the other part is transferred to the steel wire rope vibration isolator 6 of the next layer through the second steel wire rope 8. This can effectively disperse the remaining energy, allowing the impact energy to be transmitted in multiple directions. This can absorb as much energy as possible to protect the sensor from damage, and also avoid excessive energy on a single vibration damping device, which could lead to its damage, thus extending the service life of the entire vibration damping and impact-resistant device.

[0067] Example 2:

[0068] The difference from the above embodiment is that when the first wire rope 7 slides along the rubber plate 9, the included angle between the first wire rope 7 and the second wire rope 8 is α, and the range of α is 30-60°. In the initial state, the included angle between the first wire rope 7 and the second wire rope 8 is 60°.

[0069] The specific implementation process is as follows:

[0070] As the impact energy from the wire rope isolator 6 continues to be transmitted along the first wire rope 7, the initial angle between the first wire rope 7 and the second wire rope 8 is 60°. Since the force of the impact energy is primarily directed from the bracket 1 to the sensor mounting base 2, the force exerted on the first wire rope 7 causes it to slide towards the sensor. This gradually reduces the angle between the first wire rope 7 and the second wire rope 8, increasing the friction between the first wire rope 7 and the impact energy. This process absorbs the impact energy as much as possible, preventing excessive impact energy from rapidly impacting the rubber plate 9 and causing it to lose its elasticity prematurely. Furthermore, the initial state of the first wire rope 7 is set to 60° to avoid an excessively large angle. If the impact energy is applied perpendicularly to the first wire rope 7, it is easy to break the first wire rope 7, and it is also not conducive to the dispersion of impact energy along the direction of the first wire rope 7. The movement range of the first wire rope 7 is limited to forming a 30° angle with the second wire rope 8 to avoid an excessively small angle. If the impact energy is transmitted too much along the direction of the next layer of wire rope vibration isolator 6, it is not conducive to the transmission of impact energy along the direction of the first wire rope 7 to the rubber plate 9. This would result in the next layer of wire rope vibration isolator 6 bearing too much impact energy, affecting its lifespan.

[0071] Example 3:

[0072] The difference from the above embodiments is that the filling rate of silica particles 11 in the cerebrospinal fluid layer of the skull is 50%-70%.

[0073] The specific implementation process is as follows:

[0074] The filling rate of silica particles 11 in the cerebrospinal fluid layer of the skull is set to 50%-70%. Too little or too much silica particles 11 will affect the collision frequency between particles and between particles and the inner wall of the end cap 5, resulting in the impact energy not being fully absorbed.

[0075] Example 4:

[0076] The difference from the above embodiment is that adjacent wire rope vibration isolators 6 along the circumferential direction of the outer wall of the sleeve 4 are connected by a third wire rope.

[0077] The specific implementation process is as follows:

[0078] The steel wire rope vibration isolators 6 on the same layer are connected by a third steel wire rope, which allows the impact energy received by the steel wire rope vibration isolators 6 to be transmitted laterally. When the third steel wire rope is subjected to the impact energy transmitted by the steel wire rope vibration isolators 6 on both sides, they can cancel each other out after colliding because their directions are opposite, which further reduces the impact energy received by the sensor and improves the safety of the sensor.

[0079] Example 5:

[0080] The difference from the above embodiment is that the end cap 5 is bonded to the support 1 with a pressure plate 12 on the side facing the support 1. The end cap 5 has an inverted T-shaped cross section. The end cap 5 includes an integrally formed first boss and a second boss. The second boss, the pressure plate 12 and the support 1 are coaxially formed with threaded holes along the vertical axis. Several threaded holes are provided along the circumference of the second boss. The threaded holes are threadedly connected to the second bolts 13.

[0081] The specific implementation process is as follows:

[0082] A pressure plate 12 is placed between the end cap 5 and the bracket 1, and then fixedly connected by a second bolt 13, which can strengthen the whole device and prevent the device from becoming unstable when subjected to impact.

[0083] Example 6:

[0084] The difference from the above embodiments is that, as Figure 2 As shown, a vibration reduction and shock resistance method for aerospace sensors includes the following steps:

[0085] S1. Construct a vibration reduction and shock resistance system based on ANSYS finite element analysis software, and design and optimize the objective function of the wire rope vibration isolator 6 based on the vibration reduction and shock resistance system.

[0086] S2. Simulate the seismic source and measure the pre-control structural response signal of the vibration reduction and shock resistance system, as well as the frequency transfer function from the seismic source to the wire rope vibration isolator 6.

[0087] In S1 and S2, let the control objective be the sum of squares of the responses of m wire rope vibration isolators 6, e mThe structure response signal after control, d m To control the pre-structural response signal, u p For impact energy, G mp Let be the frequency transfer function, then the expression for the objective function is:

[0088] e m =d m +G mp u p ;

[0089] J = e m H e m ;

[0090] The optimal impact energy is obtained by minimizing the control objective:

[0091] u p,opt =-(G mp H G mp ) -1 G mp d m ;

[0092] The minimum value of the objective function of the vibration reduction and shock resistance system is:

[0093] J min =(d m +G mp u p,opt ) H (d m +G mp u p,opt ).

[0094] S3. Construct a fitness function based on the objective function. Select n wire rope vibration isolators 6 from the vibration reduction and shock resistance system and perform genetic algorithm iteration. Calculate the fitness function corresponding to the current iteration based on the frequency transfer function. If the fitness function of the current iteration and the previous iteration meet the set requirements, then the number and position of the selected wire rope vibration isolators 6 are taken as the optimal value, where 0 < n ≤ m.

[0095] The fitness function is expressed as follows:

[0096] F = J min +ωn;

[0097] Where ω is the weighting coefficient of the number n of the wire rope vibration isolators.

[0098] S4. Based on the number and position of the wire rope vibration isolators 6 obtained in S3, install the wire rope vibration isolators 6 on the outer wall of the sleeve 4, so that the sleeve 4 and the end cap 5 are connected, so as to complete the assembly of the woodpecker-like multi-layer vibration reduction and impact resistance structure in the vibration reduction and impact resistance system.

[0099] S5. Install bracket 1, pressure plate 12, woodpecker-inspired multi-layer vibration damping and shock-resistant structure and sensor mounting base 2 in sequence to achieve vibration damping and shock resistance for aerospace sensors based on the woodpecker head vibration damping mechanism.

[0100] This method constructs a vibration reduction and shock resistance system based on ANSYS finite element analysis software. It optimizes the number and position of the wire rope vibration isolators 6 in the woodpecker-inspired multi-layer vibration reduction and shock resistance structure, making the vibration reduction and shock resistance system in this scheme more versatile. It can adapt to different aerospace sensors for vibration reduction and shock resistance by adjusting the number and position of the wire rope vibration isolators 6.

[0101] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0102] The above descriptions are merely embodiments of the present invention. Commonly known structures and characteristics are not described in detail here. Those skilled in the art are aware of all common technical knowledge in the field prior to the application date or priority date, are aware of all existing technologies in that field, and have the ability to apply conventional experimental methods prior to that date. Those skilled in the art can, under the guidance of this application, improve and implement this solution in combination with their own capabilities. Some typical known structures or methods should not be obstacles for those skilled in the art to implement this application. It should be noted that those skilled in the art can make several modifications and improvements without departing from the structure of the present invention. These should also be considered within the scope of protection of the present invention, and will not affect the effectiveness of the implementation of the present invention or the practicality of the patent. The scope of protection claimed in this application should be determined by the content of its claims, and the specific embodiments described in the specification can be used to interpret the content of the claims.

Claims

1. A vibration reduction and shock absorption system for aerospace sensors, characterized in that: include: The bracket is installed on the housing of the aerospace equipment; Sensor mounting bracket for mounting sensors; The bracket and the sensor mounting base are fixedly connected by a first bolt. The portion of the first bolt located between the bracket and the sensor mounting base is fitted with a vibration damping and impact-resistant device. The vibration damping and impact-resistant device includes a sleeve fitted on the first bolt. The inner wall of the sleeve is threaded to the first bolt. An end cap is threaded to the middle of the outer wall of the sleeve. The end cap completely covers the lower part of the sleeve. A vibration damping and impact-resistant space is left between the outer wall of the sleeve and the inner wall of the end cap. A multi-layer vibration damping and impact-resistant structure imitating a woodpecker is provided in the vibration damping and impact-resistant space. The woodpecker-inspired multi-layered vibration-damping and shock-resistant structure includes, sequentially arranged from the outer wall of the sleeve to the inner wall of the end cap, a beak layer, a hyoid bone layer, a cancellous layer, and a skull cerebrospinal fluid layer: The beak layer includes vibration isolation groups that are evenly distributed vertically along the outer wall of the sleeve. Each vibration isolation group includes wire rope vibration isolators that are evenly distributed circumferentially along the outer wall of the sleeve. One side of the wire rope vibration isolator is hinged to the outer wall of the sleeve, and the other side of the wire rope vibration isolator is connected to the hyoid layer through a first wire rope. The first wire rope is slidably connected to the hyoid layer. Adjacent wire rope vibration isolators in the vertical direction along the outer wall of the sleeve are connected through a second wire rope. The wire rope vibration isolators, the first wire rope, and the second wire rope form a beak shape. The hyoid bone layer includes a rubber plate; The loose layer includes foam board; The cerebrospinal fluid layer of the skull includes silica particles that fill the space between the foam layer and the inner wall of the endcap.

2. The aerospace sensor vibration reduction and shock absorption system according to claim 1, characterized in that: When the first wire rope slides along the rubber plate, the angle between the first wire rope and the second wire rope is α, which varies from 30° to 60°. In the initial state, the angle between the first wire rope and the second wire rope is 60°.

3. The aerospace sensor vibration reduction and shock resistance system according to claim 1, characterized in that: The silica particle content in the cerebrospinal fluid layer of the skull is 50%-70%.

4. The aerospace sensor vibration reduction and shock resistance system according to claim 1, characterized in that: Adjacent wire rope vibration isolators along the circumference of the outer wall of the sleeve are connected by a third wire rope.

5. The aerospace sensor vibration reduction and shock resistance system according to claim 1, characterized in that: The end cap is bonded to the bracket with a pressure plate on the side facing the bracket. The end cap has an inverted T-shaped cross-section. The end cap includes an integrally formed first boss and a second boss. The second boss, the pressure plate, and the bracket are coaxially formed with threaded holes along the vertical axis. Several threaded holes are provided along the circumference of the second boss. The threaded holes are threadedly connected to a second bolt.

6. A vibration reduction and shock absorption method for aerospace sensors, based on the vibration reduction and shock absorption system for aerospace sensors according to any one of claims 1-5, characterized in that: Includes the following steps: S1. Construct a vibration reduction and shock resistance system based on ANSYS finite element analysis software, and design and optimize the objective function of the wire rope vibration isolator based on the vibration reduction and shock resistance system. S2. Simulate the seismic source and measure the pre-control structural response signal of the vibration reduction and shock resistance system, as well as the frequency transfer function from the seismic source to the wire rope vibration isolator. S3. Construct a fitness function based on the objective function. Select n wire rope vibration isolators from the vibration reduction and shock resistance system and perform genetic algorithm iteration. Calculate the fitness function corresponding to the current iteration based on the frequency transfer function. If the fitness function of the current iteration and the previous iteration meet the set requirements, then the number and position of the selected wire rope vibration isolators are taken as the optimal value, where 0 < n ≤ m. S4. Based on the number and location of the wire rope vibration isolators obtained in S3, install the wire rope vibration isolators on the outer wall of the sleeve, connect the sleeve and the end cap, and complete the assembly of the woodpecker-inspired multi-layer vibration reduction and impact resistance structure in the vibration reduction and impact resistance system. S5. Install the bracket, pressure plate, woodpecker-inspired multi-layer vibration damping and shock-resistant structure and sensor mounting base in sequence to achieve vibration damping and shock resistance for aerospace sensors based on the woodpecker head vibration damping mechanism.

7. The vibration reduction and shock resistance method for aerospace sensors according to claim 6, characterized in that: In S1 and S2, let the control objective be the sum of squares of the responses of m wire rope vibration isolators, e m The structure response signal after control, d m To control the pre-structural response signal, u p For impact energy, G mp Let be the frequency transfer function, then the expression for the objective function is: e m =d m +G mp u p ; J=e m H And m ; The optimal impact energy is obtained by minimizing the control objective: u p,opt =-(G mp H G mp ) -1 G mp d m ; The minimum value of the objective function of the vibration reduction and shock resistance system is: J min =(d m +G mp u p,opt ) H (d m +G mp u p,opt )。 8. The vibration reduction and shock resistance method for aerospace sensors according to claim 6, characterized in that: In S3, the fitness function is expressed as follows: F=J min +ωn; Where ω is the weighting coefficient of the number n of wire rope vibration isolators.

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